Laser shock peened gas turbine engine blade tip
US5620307A · kind A · utility
26Cited by
26References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 6, 1995 |
| Grant date | Apr 15, 1997 |
| Priority date | — |
| Expiry date | Mar 6, 2015 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S148/903
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
Gas turbine engine blade with a metallic airfoil having a radially outer tip extending chordwise between a leading edge and a trailing edge and at least one laser shock peened surface extending radially along at least a portion of the tip and a region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into the airfoil from the laser shock peened surface.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.